EP2161411A1 - Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion - Google Patents

Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion Download PDF

Info

Publication number
EP2161411A1
EP2161411A1 EP08015726A EP08015726A EP2161411A1 EP 2161411 A1 EP2161411 A1 EP 2161411A1 EP 08015726 A EP08015726 A EP 08015726A EP 08015726 A EP08015726 A EP 08015726A EP 2161411 A1 EP2161411 A1 EP 2161411A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
blade
section
airfoil
cross
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP08015726A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08015726A priority Critical patent/EP2161411A1/fr
Priority to PCT/EP2009/059954 priority patent/WO2010026005A1/fr
Publication of EP2161411A1 publication Critical patent/EP2161411A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods

Definitions

  • the invention relates to a turbine blade for a gas turbine, comprising a platform and a transversely disposed airfoil comprising a pressure-side airfoil wall and a suction-side airfoil wall, which airfoils at least partially define at least one cavity arranged in the interior of the airfoil. Furthermore, the invention relates to a method for producing a turbine blade with a hollow blade and a casting core for a casting device for producing such a turbine blade.
  • turbine blades are subject to vibrational excitation during operation in a gas turbine engine.
  • the vibration excitation occurs due to the rotation of the rotor to which the turbine blades are attached.
  • the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine. Therefore, care is taken in the development of the turbine blade that the finished turbine blade overall satisfies the requirements for self-resonance.
  • the object of the invention is to provide a turbine blade and the specification of a method for producing turbine blades whose natural frequency corresponds to the requirements for use within a stationary gas turbine. Another object is to provide a casting core for making such a turbine blade.
  • the object directed to the turbine blade is achieved by a turbine blade according to the features of claim 1.
  • the object directed to the method is achieved by a method for producing a turbine blade according to the features of claim 7 and the task directed to the casting core by a corresponding casting core according to the features of claim 10.
  • the invention is based on the finding that a turbine blade for a gas turbine can be adapted in terms of its natural frequency and / or rigidity, without their outer contour being changed.
  • the change in the natural frequency of the turbine blade and / or the change in the rigidity of the blade can be done in a simple manner by at least one means is provided in at least one cavity of the blade of the turbine blade, the arrangement of which mainly the change in natural frequency and / or change the rigidity of the airfoil serves.
  • the invention achieves the idea that the inner structure of a turbine blade is dictated solely by the outer aerodynamic contour of the airfoil and solely by cooling requirements typically associated with a turbine blade.
  • the invention it is proposed for the first time to provide means in the cavity of a turbine blade, which only serve to change the natural frequency of the turbine blade by changing the center of gravity of the blade and / or the stiffness of the blade compared to an identical turbine blade, but without this invention Medium.
  • the invention is thus of particular advantage for turbine blades which have already been used in gas turbines and are therefore operationally stressed. Often these turbine blades are still to be used after a gas turbine upgrade (upgrade), although due to the increased requirement of the turbine blades with regard to their natural frequency and / or with regard to the rigidity of the blade due to the upgrading of changed operating conditions of the gas turbine.
  • the invention now provides methods and means for adapting the turbine blade operated to operation to the new operating conditions independently of any possible additional refurbishment, in which case the changes take place only in the interior, that is to say in the cavity of the blade, without the aerodynamics of the blade relevant turbine blade - based on the hot air around the blade to change.
  • an insert member is mounted in the cavity thereof, wherein the arrangement of the insert member mainly serves to change the natural frequency of the turbine blade and / or the change of the stiffness of the airfoil.
  • a new casting core may also be used for a casting apparatus for producing a turbine blade, in which the casting core has successive sections which have a constant cross-section or a continuously changing cross-section along their extension, the casting core between two such sections further section with compared to substantially reduced cross-section.
  • a turbine blade according to the invention can also be manufactured in one production step.
  • the agent in question can be designed as an insert component which is manufactured separately from the airfoil and which is fastened in the cavity of the airfoil after production of the airfoil.
  • existing or already operationally loaded turbine rotor blades can be upgraded to form a turbine blade according to the invention.
  • the agent in question may also be an integral part of the airfoil so that it is made directly with the manufacture of the airfoil of the turbine blade. This is the case, for example, if at least the blade of the turbine blade, or even the entire turbine blade is produced by a casting process.
  • the airfoil is divided by means of at least one rib into a plurality of cavities, which rib extends in each case from the suction-side airfoil wall to the pressure-side airfoil wall and at the same time from a foot region of the turbine blade to an airfoil tip region.
  • the invention may thus be used in particular for turbine blades which have clean or approximately straight cooling passages which extend from a root portion of the turbine blade to a blade tip area and are separated from each other by a rib located in the interior of the airfoil.
  • turbine blades are provided on the blade tip side with an opening in the order of the cross section of the cavity arranged behind it, so that there is sufficient accessibility to the respective cavities in which the agent is to be arranged and fastened.
  • the means and / or the insert component is designed as a partition wall arranged approximately parallel to the platform of the turbine blade, in which at least one opening is formed.
  • the partition wall is thus substantially perpendicular, if present, oriented to the rib. In order to let the coolant, which generally flows in the interior of the turbine blade in the cavity, flow out or continue, at least one opening is provided in the dividing wall.
  • this can be changed in its contour, for example by means of a cutting method, to bring about a further change in the natural frequency of the turbine blade.
  • the opening can be drilled further. This makes it possible, even after the attachment of the insert component to further adjust the frequency characteristic of the turbine blade.
  • a suitably formed casting core may be used in a casting apparatus to produce a turbine blade.
  • a casting core is substantially rod-shaped with a plurality of successive sections, which along their extension either a constant cross section or a continuously changing cross-section, wherein the casting core between two such sections has a further section with compared to substantially reduced cross-section through the means in question, namely the partition, can be formed.
  • the section having a substantially reduced cross-section has a maximum cross-sectional area of 90% of the cross-sectional area of the section immediately adjacent thereto with a constant cross-section or with a continuously changing cross-section.
  • its mean cross section is to be used as a reference.
  • the cross-sectional area is to be chosen as small as possible, so that the opening formed by it, arranged in the partition opening can be reworked.
  • the transition between the further section and the immediately adjacent section with constant cross-section or with continuously changing cross-section may be step-like.
  • two or more of these further sections of substantially reduced cross-section may be present on the casting core.
  • each section having a substantially reduced cross-section is arranged on the casting core in such a way that it leaves a partition in a turbine blade made with this casting core, which is arranged in the cavity of an airfoil of the turbine blade-that is, in the interior-and not on the turbine blade tip.
  • the means to be provided which is preferably designed as a partition wall, are intended mainly to change the natural frequency of the turbine blade, to change the rigidity of the blade and / or to change the center of gravity of the blade.
  • this does not mean turbulators that are arranged on the inner side surfaces of the airfoil walls to swirl mainly the cooling air flowing along the side walls.
  • impact-cooling inserts which may, for example, be arranged inside the turbine blade in order to allow impingement cooling of the blade-blade walls.
  • ribs located inside the airfoil do not fall underneath.
  • the means according to the invention serve at least mainly, if not solely, for changing the natural frequency of the turbine blade and / or changing the rigidity of the blade compared to an identical turbine blade without such means.
  • At least as many means are provided that a change of the preferably first natural frequency of the turbine blade of at least 5 Hz, more preferably at least 10Hz - based on an identical turbine blade without the inventive means - can be brought about.
  • FIG. 1 shows a longitudinal section through a turbine blade 10 according to the invention, which along a blade main axis a foot portion 12, a hot gas platform 14 and a transversely extending, aerodynamic curved blade 16 has.
  • the airfoil 16 includes a pressure-side airfoil wall 18 (FIG. FIG. 2 ) and a suction side airfoil wall 20 extending from a common leading edge 22 to a common trailing edge 29.
  • the airfoil 16 is formed substantially hollow, wherein in FIG. 1 three cavities 24, 26, 28 are shown.
  • the cavities 24, 26 are defined by a first rib 32 and the two cavities 26, 28 are separated by a second rib 34.
  • the turbine blade 10 it is possible for the turbine blade 10 to have more than three or fewer than three cavities 24, 26, 28 and, correspondingly, more or fewer ribs 32, 34.
  • the fins 32, 34 extend from the suction side vane wall 20 to the pressure side vane wall 18 and at the same time from the root section 12 of the turbine blade 10 to the vane tip section 30.
  • the cavities 24, 26, 28 are cooling channels extending straight from the root section 12 to a tip side section 30 formed, through which a foot side supplied coolant, such as cooling air, is flowable, which can escape blade tip side.
  • the insert members 36 are formed as a partition and serve to change the natural frequency of the turbine blade 10 and / or the change in the rigidity of the airfoil 16, without having another essential function. Impact cooling inserts, rib-like turbulators or even dimplels are not included in the concept of the agents according to the invention.
  • the insert members 36 each have centrally an opening 40 through which the cavities 24, 26, 28 can flow through coolant.
  • the mass of the turbine blade 10 increases overall, a gain in stiffness can be achieved, which is the change in the natural frequency of the turbine blade 10 with respect to its self-excitation due to the hot gas occurring periodically on the airfoil 16 and / or due to the rotor speed, is further reduced.
  • the proportion of the frequency change which has a negative effect on the increase in mass is more than compensated for due to the increased stiffness.
  • insert member 36 is formed as a partition, this can be positioned by the blade tip-side, wide opening 40 of the cavities 24, 26, 28 in the interior of the blade 16 and the ribs 32, 34 and to the inner surfaces of the suction-side blade wall 20 and to the Inner surface of the pressure-side blade wall 18 are soldered or welded.
  • inventive casting core 50 is required, which is formed substantially rod-shaped and has a plurality of successive sections 52, 54, 56, 68.
  • Each of these sections 52, 54, 56, 58 has along its extent a constant cross-section or at least only slightly continuously changing cross-section, wherein the casting core 50 between two such sections 52, 54, 56, 58 another section 60 with in Compared to having significantly reduced cross-section.
  • the cross-sectional area of the reduced cross-section 60 is at most 90% of the cross-sectional area of the sections 52, 54, 56, 58 with a constant cross section or with a continuously decreasing cross section.
  • the transition between the sections 52, 54 and section 60 is effected in each case by means of a step, wherein in the illustrated example, three further sections 60 are provided with reduced cross-section. There may also be more or fewer sections 60 of reduced cross-section. If another section 60 has a particularly small cross-sectional area, this further increases the strength, in which case the remaining separating web 36 can be easily changed if necessary.
  • the casting core 50 is designed in such a way that the sections 52, 54, 56, 58 with a reduced cross-section lie in such a position that they do so Leave partitions 36, which in the interior of the cavity 24, 26, 28 of a blade 16 of the turbine blade 10 arranged cause a particularly large increase in rigidity.
  • the invention provides a turbine blade 10 for a gas turbine having a hollow airfoil 16 in which at least one means 38 is arranged to adapt the turbine blade 10 to new operating requirements, the means 38 primarily for changing the natural frequency of the turbine blade 10 and / or for changing the rigidity of the blade 16 is used.
  • the invention provides a method by means of which, after the manufacture of the blade 16, an insert component 36 is fastened in its cavity 24, 26, 28, the arrangement of which is primarily the change in the natural frequency of the turbine blade 10 and / or the change in the rigidity of the blade Blade 16 is used.
  • the diameter of the opening 40 in the separating web 36 can be increased, for example, by drilling. It is only necessary to ensure that the concomitant reduction in the mass of the turbine blade does not cause too great a change in the rigidity of the blade 16.
  • a particularly simple trained casting core 50 can be specified, through which a turbine blade 10 according to the invention can be produced particularly inexpensively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP08015726A 2008-09-05 2008-09-05 Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion Withdrawn EP2161411A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08015726A EP2161411A1 (fr) 2008-09-05 2008-09-05 Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion
PCT/EP2009/059954 WO2010026005A1 (fr) 2008-09-05 2009-07-31 Aube de turbine à fréquence propre adaptée au moyen d'un élément rapporté

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08015726A EP2161411A1 (fr) 2008-09-05 2008-09-05 Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion

Publications (1)

Publication Number Publication Date
EP2161411A1 true EP2161411A1 (fr) 2010-03-10

Family

ID=40427187

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08015726A Withdrawn EP2161411A1 (fr) 2008-09-05 2008-09-05 Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion

Country Status (2)

Country Link
EP (1) EP2161411A1 (fr)
WO (1) WO2010026005A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2792434A1 (fr) * 2013-04-19 2014-10-22 Alstom Technology Ltd Procédé de fabrication d'un composant ayant une structure d'amortissement
WO2015032936A1 (fr) * 2013-09-09 2015-03-12 Siemens Aktiengesellschaft Chambre de combustion d'une turbine à gaz et outil et procédé permettant de produire des canaux de refroidissement dans un composant d'une turbine à gaz
GB2518379A (en) * 2013-09-19 2015-03-25 Rolls Royce Deutschland Aerofoil cooling system and method
US9546552B2 (en) 2012-10-24 2017-01-17 MTU Aero Engines AG Gas turbine
US10519802B2 (en) 2012-09-28 2019-12-31 United Technologies Corporation Modulated turbine vane cooling
CN112177681A (zh) * 2020-09-21 2021-01-05 西北工业大学 一种适用于涡轮叶片内部冷却的分形间断肋结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2106996A (en) * 1981-09-30 1983-04-20 Rolls Royce Cooled rotor aerofoil blade for a gas turbine engine
EP1217171A2 (fr) * 2000-12-22 2002-06-26 General Electric Company Nervure pour influencer la fréquence propre d'une aube de turbine
DE10348413A1 (de) * 2002-10-15 2004-06-24 General Electric Company Verfahren zum Erzeugen einer Wirbelströmung auf der Innenseite von Löchern in einem Gegenstand und dazugehörige Gegenstände
EP1439281A2 (fr) * 2003-01-18 2004-07-21 Rolls-Royce Deutschland Ltd & Co KG Aube de turbine à gaz
EP1510653A2 (fr) * 2003-07-29 2005-03-02 Siemens Aktiengesellschaft Aube de turbine refroidie
DE102007015763A1 (de) * 2006-03-31 2007-10-04 General Electric Co. Verfahren und Vorrichtung zur mechanischen Fixierung nichtmetallischer Füllstoffe in Taschen

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19839592A1 (de) * 1998-08-31 2000-03-02 Asea Brown Boveri Strömungsmaschine mit gekühlter Rotorwelle
DE10064266A1 (de) * 2000-12-22 2002-07-04 Alstom Switzerland Ltd Verfahren zur Verringerung der Varianz im Kühlmediumverbrauch von Komponenten einer Strömungsmaschine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2106996A (en) * 1981-09-30 1983-04-20 Rolls Royce Cooled rotor aerofoil blade for a gas turbine engine
EP1217171A2 (fr) * 2000-12-22 2002-06-26 General Electric Company Nervure pour influencer la fréquence propre d'une aube de turbine
DE10348413A1 (de) * 2002-10-15 2004-06-24 General Electric Company Verfahren zum Erzeugen einer Wirbelströmung auf der Innenseite von Löchern in einem Gegenstand und dazugehörige Gegenstände
EP1439281A2 (fr) * 2003-01-18 2004-07-21 Rolls-Royce Deutschland Ltd & Co KG Aube de turbine à gaz
EP1510653A2 (fr) * 2003-07-29 2005-03-02 Siemens Aktiengesellschaft Aube de turbine refroidie
DE102007015763A1 (de) * 2006-03-31 2007-10-04 General Electric Co. Verfahren und Vorrichtung zur mechanischen Fixierung nichtmetallischer Füllstoffe in Taschen

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10519802B2 (en) 2012-09-28 2019-12-31 United Technologies Corporation Modulated turbine vane cooling
US9546552B2 (en) 2012-10-24 2017-01-17 MTU Aero Engines AG Gas turbine
EP2792434A1 (fr) * 2013-04-19 2014-10-22 Alstom Technology Ltd Procédé de fabrication d'un composant ayant une structure d'amortissement
WO2015032936A1 (fr) * 2013-09-09 2015-03-12 Siemens Aktiengesellschaft Chambre de combustion d'une turbine à gaz et outil et procédé permettant de produire des canaux de refroidissement dans un composant d'une turbine à gaz
CN105531544A (zh) * 2013-09-09 2016-04-27 西门子公司 用于燃气轮机的燃烧室以及用于制造燃气轮机部件中的冷却通道的方法和工具
GB2518379A (en) * 2013-09-19 2015-03-25 Rolls Royce Deutschland Aerofoil cooling system and method
CN112177681A (zh) * 2020-09-21 2021-01-05 西北工业大学 一种适用于涡轮叶片内部冷却的分形间断肋结构
CN112177681B (zh) * 2020-09-21 2022-03-15 西北工业大学 一种适用于涡轮叶片内部冷却的分形间断肋结构

Also Published As

Publication number Publication date
WO2010026005A1 (fr) 2010-03-11

Similar Documents

Publication Publication Date Title
DE602004006323T2 (de) Verfahren zur Herstellung einer Turbine mit Turbinenschaufeln unterschiedlicher Resonanzfrequenzen samt einer solchen Turbine
EP2137381B1 (fr) Procédé de fabrication d'aubes mobiles de turbine recouvertes
EP3176370B1 (fr) Ensemble d'aubes directrices pour turbomachine
DE102015219530A1 (de) Schaufel für eine Strömungsmaschine, Turbofantriebwerk und ein Verfahren zur Herstellung einer Schaufel
EP2161411A1 (fr) Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion
EP2725193B1 (fr) Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.
EP2245273B1 (fr) Aube de turbine destinée à une turbine à gaz fixe
EP1245785B1 (fr) Méthode de fabrication d' une aube de turbine
CH708438B1 (de) Turbinenschaufel.
EP2805017B1 (fr) Stator pour une turbomachine axiale et procédé de dimensionnement du stator
WO2019086065A1 (fr) Conduit intermédiaire produit par fabrication additive et destiné à être agencé entre un compresseur basse pression et un compresseur haute pression, ainsi que procédé de fabrication dudit conduit
EP1138878B1 (fr) Composant de turbine à gaz
DE10328310A1 (de) Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln
DE102009053247A1 (de) Verfahren zum Verändern einer Eigenfrequenz einer Schaufel für eine Strömungsmaschine
DE102015208784B3 (de) Herstellen von Schaufelkanälen von Turbomaschinenrotoren
EP1717416A1 (fr) Aube de turbine, utilisation et méthode de fabrication de l'aube de turbine
EP1785589A1 (fr) Aube à turbine, en particulier pour une turbine d'une centrale électrique
DE102006042647A1 (de) Turbine einer Gasturbine
WO2018069552A1 (fr) Ensemble turbomachine coulé intégralement et procédé de fabrication d'un ensemble turbomachine
EP3362648B1 (fr) Procede de fabrication d'un corps de base d'un aube de turbine
WO2010086402A2 (fr) Procédé de production d'un élément de turbine à gaz
DE102004011151A1 (de) Turbinenschaufel
DE102015226653A1 (de) Turbinenschaufel für eine thermische Strömungsmaschine
EP3085894A1 (fr) Aube et procédé de fabrication associé
DE202023106979U1 (de) Leitschaufelcluster für eine Strömungsmaschine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKY No designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100911

REG Reference to a national code

Ref country code: DE

Ref legal event code: R108

Effective date: 20110301

Ref country code: DE

Ref legal event code: 8566